4a.725 48.725-1 Provisional weight (air carrier air- Center of gravity limitations. empty weight and c. g. deter- 4a.726 Air-speed limitations. 48.727 Power-plant limitations. TRANSPORT CATEGORY AIRPLANE PERFORMANCE 4a.760-T Airplane operating manual. 4a.760-T-1 Airplane flight manuals (FAA policies which apply to § 4a.760-T). Subpart 1-Miscellaneous Requirements 4a.770 Identification plate. 4a.771 Standard weights. 4a.772 Leveling means. Appendix-Tables and Figures AUTHORITY: §§ 4a.1 to 4a.772 issued under sec. 205, 52 Stat. 984, as amended; 49 U. S. C. 425. Interpret or apply secs. 601, 603, 52 Stat. 1007, as amended, 1009, as amended, 49 U.S. C. 551, 553. SPECIAL CIVIL AIR REGULATIONS SR-399D 1. Notwithstanding any contrary provisions of the Civil Air Regulations, the Director, Bureau of Flight Standards, and any employee of such administrative unit as he shall designate may increase the maximum certificated weight for airplanes which are: (a) Operated entirely within the State of Alaska by an Alaskan air carrier or an air taxi operator pursuant to Parts 292 and 298, respectively, of the Civil Aeronautics Board's Economic Regulations, or by the United States Department of the Interior in the conduct of its game and fish law enforcement activities and its management, fire detection, and fire suppression activities concerning public lands; and (b) Type certificated under the provisions of Aeronautics Bulletin No. 7-A of the Aeronautics Branch of the United States Department of Commerce dated January 1, 1931, as amended, or under the normal category of Part 4a of the Civil Air Regulations. 2. The maximum certificated weight herein referred to shall not exceed any of the following: (a) 12,500 pounds, (b) 115 percent of the maximum weight listed in the FAA Aircraft Specification, (c) The weight at which the airplane meets the positive maneuvering load factor requirement for the normal category specified in §3.186 of the Civil Air Regulations, or (d) The weight at which the airplane meets the climb performance requirements under which it was type certificated. 3. In determining the maximum certificated weight the structural soundness of the airplane and the terrain to be traversed in the operation will be considered. 4. The maximum certificated weight so determined will be added to the airplane's operation limitations and identified as the maximum weight authorized for operations within the State of Alaska. This regulation supersedes Special Civil Air Regulation No. SR-399C, and shall terminate on October 25, 1965, unless sooner superseded or rescinded. (Secs. 313(a), 601, 603, 604; 72 Stat. 752, 775, 776, 778; 49 U.S.C. 1354, 1421, 1423, 1424) [26 F.R. 5673, June 24, 1961] SR-411A Notwithstanding the applicable structural provisions of the Civil Air Regulations, any air carrier may operate in cargo service transport category airplanes which were certificated under the provisions of Part 4a or Part 4b, effective prior to March 18, 1956, subject to the conditions hereinafter set forth: (1) The air carrier shall submit an application to the Administrator indicating its desire to operate its airplane(s) under the provisions of this special regulation, and indicating which airplane(s) would be involved. (2) The air carrier shall furnish a statement from each manufacturer for each type of airplane involved indicating in each case that the airplane manufacturer approves the operation of such type of airplane under the provisions of this regulation and that the airplane manufacturer will establish the inspection procedure prescribed in paragraph (4) of this Special Civil Air Regulation and will supervise such inspection as necessary. (3) The zero fuel weight (maximum weight of the airplane with no disposable fuel and oil) and the structural landing weight may be increased beyond the maxima approved in full compliance with the applicable Civil Air Regulations: Provided, That the Administrator of Civil Aeronautics finds that the increase in either such weight is not likely to reduce seriously the structural strength, that the probability of sudden fatigue failure is not noticeably increased, and that the flutter, deformation, and vibration characteristics do not fall below those required by the Civil Air Regulations: And provided further, That any increase in the zero fuel weight approved shall not exceed 5 percent and that the increase in the structural landing weight shall not exceed the amount, in pounds, of the increase in the zero fuel weight. (4) Airplanes for which the increased weights become effective shall be subject to inspections in addition to those normally performed, such inspections to be established by the manufacturer of the type airplane concerned, subject to the approval of the Administrator of the Federal Aviation Agency and to be supervised as found neces sary by that manufacturer, to safeguard against possible structural distress resulting from the higher operating stress levels. The air carrier shall keep for a period of at least one year, and make available upon request to the Civil Aeronautics Board, the Administrator of the Federal Aviation Agency, or the manufacturer of the type of airplane concerned, the records of such inspections. (5) Airplanes for which the increased weights become effective shall be operated in accordance with the transport category performance operating limitations prescribed in Part 40, 41, or 42 of the Civil Air Regulations, whichever is applicable. (6) The air carrier shall keep for a period of at least one year and make available upon request to the Civil Aeronautics Board, the Administrator of the Federal Aviation Agency, or the manufacturer of the type airplane concerned, records of all flights conducted at increased weights with airplanes for which the increased weights become effective, such records to include the actual take-off, zero fuel, and landing weights. (7) The Airplane Flight Manual of each airplane operating under the provisions of this special regulation shall be appropriately revised so as to include the necessary operating limitations and operating information. (8) An airplane which has been operated at increased weights under the provisions of this regulation shall not be used for the carriage of passengers, except under the following conditions: (a) Special inspections established by the manufacturer and approved by the Administrator of the Federal Aviation Agency shall have been accomplished. (b) The effects of the operations at increased weights on structural fatigue shall have been evaluated by the airplane manufacturer and taken into account in any fatigue limitations established for the airplane. This regulation shall terminate on June 30, 1962, unless sooner superseded or rescinded by the Board. [22 F. R. 4685, July 3, 1957] CROSS REFERENCES: For Special Civil Air Regulation with respect to establishing the basis for approval by the Administrator of modifications of individual DC-3 and L-18 airplanes, see SR-407 in Part 1 of this subchapter. For Special Civil Air Regulation with respect to performance credit for use of standby power on transport category airplanes, see SR-426 in Part 1 of this subchapter. Subpart A-Airworthiness SOURCE: §§ 4a.1 to 4a.31-1 contained in Amendment 48, 5 F. R. 1834, May 22, 1940, as amended by Amendment 75, 5 F. R. 3946, Oct. 8, 1940; 24 F.R. 5, Jan. 1, 1959, except as otherwise noted. |